AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 33.32 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-50000-n5.txt Download as CSV file: xf-ag46ct02r-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG46ct -02f rot.
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4638 0.09353 0.08725 0.0071 1.0000 0.1074
-7.750 -0.4653 0.08700 0.08070 0.0031 1.0000 0.0678
-7.500 -0.4667 0.08168 0.07541 0.0006 1.0000 0.0552
-7.000 -0.5431 0.08384 0.07728 0.0002 1.0000 0.0539
-6.750 -0.5279 0.07581 0.06912 -0.0119 1.0000 0.0455
-6.500 -0.5170 0.07178 0.06506 -0.0121 1.0000 0.0442
-6.250 -0.5033 0.06709 0.06031 -0.0147 1.0000 0.0429
-6.000 -0.4873 0.06207 0.05517 -0.0181 1.0000 0.0416
-5.750 -0.4690 0.05689 0.04981 -0.0214 1.0000 0.0404
-5.500 -0.4487 0.05174 0.04437 -0.0244 1.0000 0.0394
-5.250 -0.4265 0.04686 0.03912 -0.0268 1.0000 0.0389
-5.000 -0.4029 0.04264 0.03448 -0.0285 1.0000 0.0400
-4.750 -0.3778 0.03878 0.03011 -0.0297 1.0000 0.0418
-4.500 -0.3515 0.03520 0.02594 -0.0304 1.0000 0.0433
-4.250 -0.3244 0.03196 0.02212 -0.0306 1.0000 0.0440
-4.000 -0.2968 0.02914 0.01872 -0.0304 1.0000 0.0450
-3.750 -0.2697 0.02663 0.01578 -0.0300 1.0000 0.0470
-3.500 -0.2437 0.02495 0.01397 -0.0297 1.0000 0.0535
-3.250 -0.2163 0.02321 0.01187 -0.0288 1.0000 0.0593
-3.000 -0.1900 0.02165 0.01026 -0.0282 1.0000 0.0677
-2.750 -0.1634 0.02040 0.00886 -0.0275 1.0000 0.0846
-2.500 -0.1368 0.01908 0.00763 -0.0272 1.0000 0.1155
-2.250 -0.1106 0.01746 0.00654 -0.0271 1.0000 0.2107
-2.000 -0.0918 0.01526 0.00601 -0.0257 1.0000 0.5245
-1.750 -0.0562 0.01388 0.00542 -0.0246 1.0000 1.0000
-1.500 -0.0307 0.01384 0.00499 -0.0242 1.0000 1.0000
-1.250 -0.0054 0.01382 0.00462 -0.0238 1.0000 1.0000
-1.000 0.0197 0.01382 0.00436 -0.0234 1.0000 1.0000
-0.750 0.0446 0.01383 0.00418 -0.0230 1.0000 1.0000
-0.500 0.0692 0.01387 0.00406 -0.0226 1.0000 1.0000
-0.250 0.0934 0.01394 0.00398 -0.0223 1.0000 1.0000
0.000 0.1172 0.01404 0.00400 -0.0220 1.0000 1.0000
0.250 0.1404 0.01419 0.00410 -0.0217 1.0000 1.0000
0.500 0.1742 0.01441 0.00428 -0.0237 0.9863 1.0000
0.750 0.2229 0.01462 0.00442 -0.0282 0.9501 1.0000
1.000 0.2685 0.01480 0.00456 -0.0317 0.9119 1.0000
1.250 0.3097 0.01497 0.00468 -0.0339 0.8724 1.0000
1.500 0.3451 0.01516 0.00481 -0.0348 0.8330 1.0000
1.750 0.3752 0.01541 0.00495 -0.0344 0.7961 1.0000
2.000 0.4020 0.01571 0.00512 -0.0334 0.7620 1.0000
2.250 0.4272 0.01606 0.00534 -0.0320 0.7302 1.0000
2.500 0.4519 0.01645 0.00564 -0.0308 0.6989 1.0000
2.750 0.4764 0.01683 0.00602 -0.0296 0.6660 1.0000
3.000 0.5008 0.01716 0.00634 -0.0285 0.6322 1.0000
3.250 0.5251 0.01748 0.00662 -0.0273 0.5980 1.0000
3.500 0.5493 0.01782 0.00691 -0.0261 0.5625 1.0000
3.750 0.5734 0.01817 0.00728 -0.0249 0.5259 1.0000
4.000 0.5977 0.01856 0.00764 -0.0238 0.4864 1.0000
4.250 0.6218 0.01900 0.00803 -0.0228 0.4455 1.0000
4.500 0.6458 0.01952 0.00848 -0.0219 0.4038 1.0000
4.750 0.6700 0.02013 0.00901 -0.0211 0.3618 1.0000
5.000 0.6944 0.02084 0.00972 -0.0205 0.3213 1.0000
5.250 0.7187 0.02166 0.01048 -0.0200 0.2836 1.0000
5.500 0.7427 0.02258 0.01134 -0.0195 0.2495 1.0000
5.750 0.7663 0.02359 0.01232 -0.0190 0.2201 1.0000
6.000 0.7900 0.02469 0.01350 -0.0185 0.1940 1.0000
6.250 0.8133 0.02586 0.01474 -0.0180 0.1703 1.0000
6.500 0.8360 0.02716 0.01605 -0.0173 0.1516 1.0000
6.750 0.8589 0.02852 0.01758 -0.0168 0.1323 1.0000
7.000 0.8814 0.03010 0.01933 -0.0161 0.1174 1.0000
7.250 0.9032 0.03173 0.02113 -0.0155 0.1031 1.0000
7.500 0.9246 0.03361 0.02329 -0.0148 0.0912 1.0000
7.750 0.9453 0.03575 0.02561 -0.0141 0.0823 1.0000
8.000 0.9644 0.03757 0.02756 -0.0136 0.0725 1.0000
8.250 0.9829 0.04091 0.03153 -0.0128 0.0664 1.0000
8.500 1.0000 0.04331 0.03409 -0.0122 0.0607 1.0000
8.750 1.0116 0.04712 0.03854 -0.0118 0.0554 1.0000
9.000 1.0211 0.05100 0.04290 -0.0114 0.0519 1.0000
9.250 1.0285 0.05487 0.04710 -0.0112 0.0498 1.0000
9.500 1.0347 0.05862 0.05095 -0.0110 0.0479 1.0000
9.750 1.0255 0.06428 0.05715 -0.0118 0.0472 1.0000
10.000 1.0111 0.07002 0.06324 -0.0135 0.0470 1.0000
10.250 0.9929 0.07566 0.06907 -0.0160 0.0472 1.0000
10.500 0.9752 0.08229 0.07580 -0.0208 0.0476 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG46ct -02f rot. (ag46ct02r-il)